Attitude determination and control system of Sathyabamasat

Rani B.S., Gomathy C., Sowmya B., Narmadha R.
Sathyabama University, Chennai-119, India

Abstract: A high-precision attitude determination and control of the sathyabama satellite is an essential task for the success of the whole mission. Satellite Attitude determination and control system is an integral part of any satellite. For satellites in LEO an interaction with the local geomagnetic field is an important means of controlling the attitude or orientation. Attitude estimation is highly nonlinear due to the inherent nonlinearity in rotational kinematics, satellite attitude dynamics, and the nature of information through sensors, such as magnetometers. For attitude control, actuators must be based primarily on space and weight minimization. It uses three magnetic torque coils which are oriented orthogonally to each other. This paper describes the attitude determination and control in a closed loop configuration. © 2010 IEEE.
Author Keywords: ADCS; Attitude control; Attitude determination; Sathyabamasat

Year: 2010
Source title: Proceedings of the International Conference on "Recent Advances in Space Technology Services and Climate Change - 2010", RSTS and CC-2010
Art. No.: 5712821
Page : 326-329
Link: Scorpus Link
Document Type: Conference Paper
Source: Scopus
Authors with affiliations:

1. Rani, B.S., Sathyabama University, Chennai-119, India
2. Gomathy, C., Sathyabama University, Chennai-119, India
3. Sowmya, B., Sathyabama University, Chennai-119, India
4. Narmadha, R., Sathyabama University, Chennai-119, India

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